FIELD: engines and pumps.
SUBSTANCE: low-thrust rocket engine has the main chamber formed inside the pipe. Pipe has longitudinal axis determining the thrust axis. Injector supplies ionised gas to the pipe on one end of the main chamber. Ioniser ionises the introduced gas in the main chamber. The first generator of magnetic field and generator of electromagnetic field create the accelerating field of ponderomotive force determined with magnetic fields, after ioniser along thrust direction along the axis. Low-thrust rocket engine ionises gas and then accelerates electrons and ions under action of ponderomotive force determined with magnetic fields.
EFFECT: invention allows increasing the jet flow velocity at mass expulsion, and efficiency of rocket engine respectively.
71 cl, 40 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SPACECRAFT LOW-THRUST ENGINE | 2004 |
|
RU2330181C2 |
| RAMJET RELATIVISTIC ENGINE | 2020 |
|
RU2776324C1 |
| WAVE ION ENGINE WITH A CLOSED GAS DISCHARGE CHAMBER | 2021 |
|
RU2771908C1 |
| IONIC ROCKET ENGINE OF SPACECRAFT | 2018 |
|
RU2682962C1 |
| HYBRID WAVE PLASMA ENGINE FOR LOW ORBIT SPACE VEHICLE | 2021 |
|
RU2764487C1 |
| METHOD OF THRUSTING AND DESIGN OF JET ENGINE | 1997 |
|
RU2169854C2 |
| MODULE WITH MULTICHANNEL PLASMA PROPULSION SYSTEM FOR SMALL SPACECRAFT | 2020 |
|
RU2741401C1 |
| DEVICE FOR MEASUREMENT OF CHANGE IN THRUST OF PLASMA JET ENGINE WITH CLOSED ELECTRODE DRIFT | 1993 |
|
RU2107186C1 |
| PLASMA ENGINE AND METHOD OF GENERATING ACTUATING PLASMA TRACTION | 2012 |
|
RU2610162C2 |
| BIDIRECTIONAL WAVE PLASMA ENGINE FOR A SPACE VEHICLE | 2020 |
|
RU2764823C1 |
